An integrated separation system and interface structure is disclosed for a variety of deployment applications. In one embodiment, a Universal Spacecraft Separation Node (100) includes a separation nut assembly (102), a separation spring assembly (104) an LV node fitting (106) and an SC node fitting (108). The LV node fitting (106) is connected to a launch vehicle (210) and the SC node fitting (108) is connected to a spacecraft (216). The separation nut assembly (102) holds the fittings (106 and 108) together until separation is desired. Upon separation, the separation spring assembly (104) provides a force to urge the launch vehicle (210) and spacecraft (216) apart. Prior to separation, an annular tongue (224) of fitting (108) mates with an annular groove (226) of fitting (106) to resist shear forces.